EP2551189B1 - Protective shield against ice impacts on aircraft - Google Patents

Protective shield against ice impacts on aircraft Download PDF

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Publication number
EP2551189B1
EP2551189B1 EP12176471.6A EP12176471A EP2551189B1 EP 2551189 B1 EP2551189 B1 EP 2551189B1 EP 12176471 A EP12176471 A EP 12176471A EP 2551189 B1 EP2551189 B1 EP 2551189B1
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EP
European Patent Office
Prior art keywords
aircraft
healing agent
healing
protective shield
microcapsules
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP12176471.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2551189A2 (en
EP2551189A3 (en
Inventor
Julien Guillemaut
Tamara BLANCO VARELA
Diego FOLCH CORTÉS
Pablo Goya Albaurrea
Esteban MARTINO GONZÁLEZ
Eduardo Vinue Santolalla
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SL
Original Assignee
Airbus Operations SL
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Filing date
Publication date
Application filed by Airbus Operations SL filed Critical Airbus Operations SL
Publication of EP2551189A2 publication Critical patent/EP2551189A2/en
Publication of EP2551189A3 publication Critical patent/EP2551189A3/en
Application granted granted Critical
Publication of EP2551189B1 publication Critical patent/EP2551189B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/16—Auto-repairing or self-sealing arrangements or agents
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/16—Auto-repairing or self-sealing arrangements or agents
    • B29C73/22—Auto-repairing or self-sealing arrangements or agents the article containing elements including a sealing composition, e.g. powder being liberated when the article is damaged
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K9/00—Use of pretreated ingredients
    • C08K9/10—Encapsulated ingredients
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L63/00—Compositions of epoxy resins; Compositions of derivatives of epoxy resins

Definitions

  • This invention discloses a shield protection against ice impact for aircraft, especially propelled engine aircraft. It is included in the technical field of the aeronautical industry.
  • Propelled engine aircraft are very common as transportation means, both in military and civil applications (for cargo or passengers use), in short and medium distances. Under certain weather conditions, propellers may expel ice fragments against the aircraft fuselage; the invention discloses a shield against ice impact on the aircraft fuselage using self-healing materials.
  • Shields for aircraft fuselages are used to protect aircraft structures due to ice or other objects which may impact on the aircraft surface.
  • the size of the ice fragments and the number of ice impacts may depend on the time spent by the aircraft within icing conditions.
  • Most modern aircraft also have de-icing systems, including propeller de-icing devices, which reduce the severity of ice impacts during nominal flight.
  • de-icing systems including propeller de-icing devices, which reduce the severity of ice impacts during nominal flight.
  • the case of a de-icing system failure during in-flight conditions must also be taken into account (in spite of a lower probability of occurrence).
  • the ice impacts might be more severe and the probability to get repetitive impacts is real (because the aircraft might stay a long time in icing conditions with non-operative de-icing systems).
  • ice fragments may be expelled by the propellers, impacting the aircraft fuselage or other relevant parts of the airplane (for instance, vertical and horizontal tail planes). Consequently, a shielding protection is required to minimize in-flight damage of such aircraft parts. Because ice impacts may occur a lot (even during the same flight), it is necessary to define a robust protection against that kind of threat, in order to reduce the operating costs of the company. This is the objective of the invention.
  • Document WO 2007/003879 A1 discloses a self healing structure comprising a solid fibre material embedded in a resin matrix, providing repair facility by the use of curable two-part adhesive compositions in some of the fibres of the structure.
  • Document GB 2 288 441 A reveals a propeller comprising a blade of multiple layer fibre-bond design and a protective contour attached along the blade. Nevertheless, no evidence about a shield for aircraft fuselages using self-healing materials according to the present invention has been found.
  • the invention has developed a protective shield against ice impacts on aircraft structures according to the disclosure of claim 1.
  • This shield comprises plies of composite material having microcapsules, each microcapsule containing a healing agent.
  • the microcapsules are made of urea-formaldehyde or polyvinyl alcohol.
  • the composite material of the shield also has other microcapsules containing catalyst particles, and the healing agent contained in a microcapsule actuates when a crack produced at the shield reaches:
  • the catalyst particles react with the healing agent, such healing agent becoming a polymerized healing agent.
  • the healing agent according to a disclosure not being part of the invention may be dicyclopentadiene; for this healing agent the catalyst particles reacting with it are tungsten hexachloride and diethyaluminum chloride (WCl 6 -Et 2 AlCl) particles, or ruthenium carbene complexes particles, or osmiun carbene complexes particles.
  • the healing agent according to the invention is cyanoacrilate.
  • the catalyst particles (3) are water particles.
  • the healing agent contained in the microcapsules is a thermoplastic polymer, but there are no other microcapsules with catalyst particles.
  • the healing agent contained in the microcapsules becomes liquid when heating the shielding panels, spreading the healing agent within the crack. Then, when the temperature of the shielding panels decreases the healing agent turns back into a solid, hardening the crack.
  • the shielding panels are manufactured using an epoxy resin, a bismaleimide (BMI) resin, or a thermoplastic resin (like PEEK (poly-ether-ether-ketone) resin or like PEKK (poly-ether-ketone-ketone) resin).
  • the invention also discloses a protective shield against ice impacts on aircraft structures, wherein the shield has shielding panels assembled on vertical and horizontal frames that are attached to the aircraft structure.
  • This aircraft structure may be a part of a fuselage section, a vertical tail plane, a horizontal tail plane, an engine nacelle, or a pylon.
  • 1 composite material
  • 2 microcapsules
  • 3 catalyst particles
  • 4 crack
  • 5 healing agent
  • 6 polymerized healing agent
  • 7 main fuselage
  • 8 frames
  • 9 shielding panels
  • 10 rear fuselage
  • 11 pylon
  • 12 vertical tail plane
  • 13 horizontal tail plane
  • 14 engine
  • 15 engine nacelle.
  • Figure 1 shows a sectional cross view of a composite material according to the first embodiment of "self-healing materials" presented in this invention.
  • Figure 1.a represents several plies of composite material (1) (the plies cannot be represented at this scale) having microcapsules (2). Some microcapsules (2) contain a healing agent (5) (usually adhesive material), and some microcapsules (2) contain catalysts particles (3). In figure 1 only the microcapsules (2) containing the healing agent (5) have been represented with their numerical reference; therefore, it must be understood that the catalyst particles (3) are also contained in their correspondent microcapsule (2).
  • Figure 1.a) also shows the situation when a crack (4) begins to grow inside the composite material (1). This may occur for example when an ice fragment impact against the shield.
  • Figure 1.b) represents the situation when the crack (4) reaches a microcapsule (2).
  • the healing agent (5) is spread within the crack (4).
  • Figure 1.c) represents how the healing agent (5) actuates.
  • This healing agent (5) is a monomeric healing agent that reacts in the presence of the catalyst particles (3), filling the crack (4) with a polymerized healing agent (6) that is generated due to the reaction of the healing agent (5) with the catalyst particles (3).
  • the healing agent (5) can be, according to a disclosure not being part of the invention, dicyclopentadiene (DCPD) or, according to a disclosure being part of the invention, cyanoacrilate.
  • the microcapsules (2) may be formed of urea-formaldehyde (UF) or polyvinyl alcohol (PVA) components.
  • the catalyst particles (3) are also contained in microcapsules having similar characteristics to the microcapsules (2) containing the healing agent (5). There are several options when choosing catalyst particles (3).
  • the catalyst particles (3) may be: a) a catalyst system based on tungsten hexachloride and diethyaluminum chloride (WCl 6 -Et 2 AlCl), or b) a catalyst system based on ruthenium carbene complexes or c) a catalyst system based on osmiun carbene complexes.
  • the healing agent (5) and the catalyst particles (3) which are contained inside the microcapsules (2), are operative when liquid. If the healing agent (5) and the catalyst particles (3) are maintained in a liquid state when the crack is produced, the healing process will be realized immediately according to the previous explanations. If the healing agent (5) and the particles (3) are not maintained in a liquid state when the crack is produced, the healing process will be in a stand-by state until the conditions (temperature and pressure) are recovered.
  • the catalyst particles (3) may be water (specifically hydroxide ions). According to this configuration, the microcapsules (2) containing the catalyst particles (3) are filled up with liquid water or water steam for example.
  • the microcapsules (2) contain self-healing materials (thermoplastic polymers like paraffin) that generate a healing process when heated, but no catalyst particles (3) are contained inside the composite material.
  • self-healing materials thermoplastic polymers like paraffin
  • Such kind of materials have the same function as the first kind of self-healing materials, the microcapsule (2) breaks because of the crack (4) growth, but the activation process is different.
  • the shield must be warmed up to activate the healing process, and this heating process makes the thermoplastic polymer (like paraffin) fill the crack (4).
  • the thermoplastic polymer (like paraffin) which is used usually melts between 70 oC and 80 oC.
  • the activation of the healing process is done on ground, when the after-flight inspection has detected damage of the shields.
  • the healing agent (5) should melt at a temperature lower than the microcapsules (2) melting temperature.
  • the healing agent (5) melting temperature must also be lower than the glass transition temperature (Tg) of the resin integrating the composite material (1).
  • the reaction of the healing agent (5), a thermoplastic polymer (like paraffin), is a two step process.
  • the healing agent (5) becomes liquid, and this fluidity makes the healing agent (5) spread within the crack (4).
  • the healing agent (5) turns back into a solid, hardening the crack (4).
  • this second embodiment is a singular case of the first embodiment, wherein the catalyst particles (3) are substituted by a heat flow.
  • the shields disclosed in this invention are suitable for being used in several aircraft types, including rotary wing aircraft such as helicopters and fixed wing aircraft as well. These shields protecting the aircraft surface may have several configurations; figures 2 , 3 and 4 present some of these configurations.
  • the composite material (1) is placed as a shield on a structure above the aircraft fuselage. This situation is shown in figure 2 that represents an aircraft fuselage (7) with shielding panels (9). Such panels (9) are mounted on vertical and horizontal frames (8) (see figure 3.1 ) that are attached to the fuselage (7) in a conventional manner. Depending on the fuselage (7) area that is covered by the shield panels (9), such panels (9) adopt different geometric configurations ( figure 3.2 ).
  • the shielding panels (9) may have other configurations that are shown in figure 4 .
  • FIG 4 another example of a rear-mounted engine aircraft with different possible locations for shielding panels (9) is presented.
  • the shielding panels (9) are located on the rear fuselage (10) panels (outside).
  • the shielding panels (9) are located on the vertical tail plane (12), although other alternative locations on the horizontal tail plane (13) are possible as well.
  • Figure 4.3 represents the shielding panels (9) located on the pylon (11) structure and the engine nacelle (15).
  • the shielding panels (9) are assembled on vertical and horizontal frames (8) that are attached to the aircraft structure.
  • Such aircraft structure may be a fuselage section, like the main fuselage (7) or the rear fuselage (10) ( figure 4.1 ).
  • the shielding panels (9) can also be assembled on other aircraft structure elements, like the engine pylon (11) ( figure 4.3 ), the vertical tail plane (12) and the horizontal tail plane (13) ( figure 4.2 ), and the engine nacelle (15).
  • the protection given by the engine nacelle (15) may be especially important in some engines (14) having propellers, like the UDF (unducted fan) engines (see figure 4.3 ).
  • the resin of the composite material used is an epoxy resin, bismaleimide (BMI) resin, thermoplastic resin (like PEEK (poly-ether-ether-ketone) or PEKK (poly-ether-ketone-ketone) resin) or other similar resins.
  • the fibre used may be one of the generally known ones for aeronautical applications such as glass fibre, carbon fibre or Kevlar®, using several geometric configurations like one-dimensional, two-dimensional or three-dimensional woven fibres. These materials may be "pre-impregnated” (also called “prepreg”) or the resin may be introduced by "infusion”.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Medicinal Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Health & Medical Sciences (AREA)
  • Polymers & Plastics (AREA)
  • Organic Chemistry (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Laminated Bodies (AREA)
  • Vibration Dampers (AREA)
  • Manufacturing Of Micro-Capsules (AREA)
  • Professional, Industrial, Or Sporting Protective Garments (AREA)
EP12176471.6A 2011-07-29 2012-07-13 Protective shield against ice impacts on aircraft Active EP2551189B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ES201131330A ES2395645B1 (es) 2011-07-29 2011-07-29 Escudo protector contra impactos de hielo en aeronaves.

Publications (3)

Publication Number Publication Date
EP2551189A2 EP2551189A2 (en) 2013-01-30
EP2551189A3 EP2551189A3 (en) 2013-05-29
EP2551189B1 true EP2551189B1 (en) 2016-08-31

Family

ID=46516582

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12176471.6A Active EP2551189B1 (en) 2011-07-29 2012-07-13 Protective shield against ice impacts on aircraft

Country Status (6)

Country Link
US (1) US20130187002A1 (es)
EP (1) EP2551189B1 (es)
CN (1) CN102897312A (es)
CA (1) CA2783317C (es)
ES (2) ES2395645B1 (es)
RU (1) RU2607686C2 (es)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2395645B1 (es) * 2011-07-29 2013-12-16 Airbus Operations, S.L. Escudo protector contra impactos de hielo en aeronaves.
WO2015171429A1 (en) * 2014-05-07 2015-11-12 Wichita State University Nanocomposite microcapsules for self-healing of composite articles
US11358736B2 (en) * 2017-11-07 2022-06-14 Leonardo S.P.A. System for enhancing the structural resilience of an aircraft, and aircraft comprising such system
CN111843375B (zh) * 2020-07-31 2021-12-21 中山市方威金属科技有限公司 一种不锈钢工件裂纹修复用熔融修补方法
CH719352A1 (fr) * 2022-01-11 2023-07-31 Comppair Tech Sa Matériaux multicouches autoréparables.

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Also Published As

Publication number Publication date
CA2783317C (en) 2019-09-24
CN102897312A (zh) 2013-01-30
US20130187002A1 (en) 2013-07-25
RU2607686C2 (ru) 2017-01-10
ES2395645B1 (es) 2013-12-16
EP2551189A2 (en) 2013-01-30
CA2783317A1 (en) 2013-01-29
RU2012132407A (ru) 2014-02-10
EP2551189A3 (en) 2013-05-29
ES2395645A1 (es) 2013-02-14
ES2606372T3 (es) 2017-03-23

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